전산유체역학을 이용한 SDM의 세로 동안정성 미계수 예측

초록

This study focuses on the computation of longitudinal dynamic derivatives for a full aircraft configuration. For the study, a new CFD code based on the non-inertial coordinate method are developed. For the validation of the code, steady circular motions of NACA 0012 airfoil at constant pitch rates are simulated, and their results are compared to the experimental data as well as known computational results. The code is applied to a full aircraft configuration. the SDM(Standard Dynamic Model) for damping coefficients. Pitch damping coefficients of SDM are derived from steady circular motion, and compared to the experimental and numerical results.